RU2005112913A - GAS TURBINE RING HOUSING AND RING HOUSING SEGMENT - Google Patents

GAS TURBINE RING HOUSING AND RING HOUSING SEGMENT Download PDF

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Publication number
RU2005112913A
RU2005112913A RU2005112913/06A RU2005112913A RU2005112913A RU 2005112913 A RU2005112913 A RU 2005112913A RU 2005112913/06 A RU2005112913/06 A RU 2005112913/06A RU 2005112913 A RU2005112913 A RU 2005112913A RU 2005112913 A RU2005112913 A RU 2005112913A
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RU
Russia
Prior art keywords
radial
axial
segment
groove
ring housing
Prior art date
Application number
RU2005112913/06A
Other languages
Russian (ru)
Other versions
RU2373401C2 (en
Inventor
Ален ЖЕНДРО (FR)
Ален ЖЕНДРО
Дельфин РУССЕН-МОЙНЬЕ (FR)
Дельфин РУССЕН-МОЙНЬЕ
Original Assignee
Снекма Моторс (Fr)
Снекма Моторс
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication date
Application filed by Снекма Моторс (Fr), Снекма Моторс filed Critical Снекма Моторс (Fr)
Publication of RU2005112913A publication Critical patent/RU2005112913A/en
Application granted granted Critical
Publication of RU2373401C2 publication Critical patent/RU2373401C2/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements

Claims (6)

1. Неподвижный кольцевой компонент, образующий оболочку, охватывающую ротор газовой турбины, и содержащий сегменты (16, 18), смежные боковые грани (30, 40) которых соединены встык через средства уплотнения, причем средства уплотнения содержат, по меньшей мере, одну осевую уплотняющую вставку (42) и, по меньшей мере, одну радиальную уплотняющую вставку (44), расположенные соответственно в, по меньшей мере, одном осевом пазе (26, 36) и в, по меньшей мере, одном радиальном пазе (28, 38), предусмотренных напротив друг друга в смежных боковых гранях сегментов, причем радиальный паз (28, 38) примыкает, по меньшей мере, одним из своих концов к осевому пазу (26, 36), отличающийся тем, что осевой паз (26, 36) каждого сегмента (16, 18) имеет глубину (Р1), большую, чем глубина (Р2) радиального паза (28, 38), а осевая уплотняющая вставка (42) имеет ширину (L1), большую, чем ширина (L2) радиальной уплотняющей вставки (44).1. A fixed annular component forming a shell covering the rotor of a gas turbine and containing segments (16, 18), adjacent side faces (30, 40) of which are joined end-to-end through sealing means, the sealing means containing at least one axial sealing an insert (42) and at least one radial sealing insert (44) located respectively in at least one axial groove (26, 36) and in at least one radial groove (28, 38), provided opposite to each other in adjacent side faces of the segments, with eat a radial slot (28, 38) is adjacent to at least one of its ends to an axial groove (26, 36), characterized in that the axial slot (26, 36) of each segment (16, 18) has a depth (P1) greater than the depth ( P2 ) of the radial groove (28, 38), and the axial sealing insert (42) has a width ( L1 ) greater than the width ( L2 ) of the radial sealing insert (44). 2. Компонент по п.1, отличающийся тем, что образует кольцо турбины высокого давления турбомашины.2. The component according to claim 1, characterized in that it forms a ring of the high pressure turbine of the turbomachine. 3. Компонент по п.2, отличающийся тем, что боковые грани (30) каждого кольцевого сегмента (16) содержат по два осевых паза (26), которые расположены со стороны внутренней стенки (32а) и внешней стенки (32b), и в которых расположены осевые вставки, и по два радиальных паза (28), которые расположены со стороны передней стенки (34а) и задней стенки (34b) и в которых расположены радиальные вставки.3. A component according to claim 2, characterized in that the side faces (30) of each annular segment (16) contain two axial grooves (26), which are located on the side of the inner wall (32a) and the outer wall (32b), and which are axial inserts, and two radial grooves (28), which are located on the side of the front wall (34a) and the rear wall (34b) and in which the radial inserts are located. 4. Компонент по п.1, отличающийся тем, что образует перемычку турбины высокого давления турбомашины.4. The component according to claim 1, characterized in that it forms a jumper of the high pressure turbine of the turbomachine. 5. Компонент по п.4, отличающийся тем, что боковые грани (40) каждого сегмента (18) перемычки содержат по одному осевому пазу (36), в котором расположена осевая вставка (42), и, по меньшей мере, по три радиальных паза (38), два из которых расположены со стороны передней стенки (22а) и задней стенки (22b), в которых расположены радиальные вставки (44).5. A component according to claim 4, characterized in that the lateral faces (40) of each segment (18) of the jumper contain one axial groove (36) in which the axial insert (42) is located, and at least three radial a groove (38), two of which are located on the side of the front wall (22a) and the rear wall (22b), in which the radial inserts (44) are located. 6. Сегмент (16, 18) неподвижного кольцевого компонента (12) газовой турбины, заявленного в любом из пп.1-5.6. A segment (16, 18) of a fixed annular component (12) of a gas turbine, as claimed in any one of claims 1 to 5.
RU2005112913/06A 2004-05-04 2005-04-28 Gas turbine stator circular housing and circular housing segment RU2373401C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0404737A FR2869943B1 (en) 2004-05-04 2004-05-04 FIXED RING ASSEMBLY OF A GAS TURBINE
FR0404737 2004-05-04

Publications (2)

Publication Number Publication Date
RU2005112913A true RU2005112913A (en) 2006-11-20
RU2373401C2 RU2373401C2 (en) 2009-11-20

Family

ID=34942095

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2005112913/06A RU2373401C2 (en) 2004-05-04 2005-04-28 Gas turbine stator circular housing and circular housing segment

Country Status (9)

Country Link
US (1) US7201559B2 (en)
EP (1) EP1593814B1 (en)
JP (1) JP4516473B2 (en)
CA (1) CA2504171C (en)
DE (1) DE602005008503D1 (en)
ES (1) ES2311201T3 (en)
FR (1) FR2869943B1 (en)
RU (1) RU2373401C2 (en)
UA (1) UA87971C2 (en)

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US8753073B2 (en) 2010-06-23 2014-06-17 General Electric Company Turbine shroud sealing apparatus
US20120128472A1 (en) * 2010-11-23 2012-05-24 General Electric Company Turbomachine nozzle segment having an integrated diaphragm
FR2968350B1 (en) * 2010-12-06 2016-01-29 Snecma SECTORIZED TURBINE RING FOR TURBOMACHINE, AND TURBOMACHINE EQUIPPED WITH SUCH A RING
US8444152B2 (en) * 2011-05-04 2013-05-21 General Electric Company Spring seal assembly and method of sealing a gap
US20120292856A1 (en) * 2011-05-16 2012-11-22 United Technologies Corporation Blade outer seal for a gas turbine engine having non-parallel segment confronting faces
GB201117084D0 (en) * 2011-10-05 2011-11-16 Rolls Royce Plc Strip seals
US9810086B2 (en) * 2011-11-06 2017-11-07 General Electric Company Asymmetric radial spline seal for a gas turbine engine
US9587746B2 (en) 2012-07-31 2017-03-07 General Electric Company Film riding seals for rotary machines
US9416671B2 (en) 2012-10-04 2016-08-16 General Electric Company Bimetallic turbine shroud and method of fabricating
US10161259B2 (en) 2014-10-28 2018-12-25 General Electric Company Flexible film-riding seal
FR3041993B1 (en) * 2015-10-05 2019-06-21 Safran Aircraft Engines TURBINE RING ASSEMBLY WITH AXIAL RETENTION
US10822988B2 (en) * 2015-12-21 2020-11-03 Pratt & Whitney Canada Corp. Method of sizing a cavity in a part
US10655495B2 (en) 2017-02-24 2020-05-19 General Electric Company Spline for a turbine engine
US10662794B2 (en) * 2017-10-19 2020-05-26 Rolls-Royce Corporation Strip seal axial assembly groove
GB2571802A (en) * 2018-03-06 2019-09-11 Rolls Royce Plc A Gas Turbine Engine Combustion Arrangement and a Gas Turbine Engine
RU190280U1 (en) * 2019-01-09 2019-06-25 Публичное Акционерное Общество "Одк-Сатурн" DEVICE FOR FIXING SEGMENT OF SEGPLATES IN THE FORCE CASE OF A TURBINE STATOR
US11111802B2 (en) * 2019-05-01 2021-09-07 Raytheon Technologies Corporation Seal for a gas turbine engine

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Also Published As

Publication number Publication date
EP1593814B1 (en) 2008-07-30
RU2373401C2 (en) 2009-11-20
FR2869943A1 (en) 2005-11-11
FR2869943B1 (en) 2006-07-28
UA87971C2 (en) 2009-09-10
JP2005320965A (en) 2005-11-17
ES2311201T3 (en) 2009-02-01
DE602005008503D1 (en) 2008-09-11
EP1593814A1 (en) 2005-11-09
US7201559B2 (en) 2007-04-10
CA2504171A1 (en) 2005-11-04
US20050248100A1 (en) 2005-11-10
CA2504171C (en) 2012-10-23
JP4516473B2 (en) 2010-08-04

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PD4A Correction of name of patent owner
MM4A The patent is invalid due to non-payment of fees

Effective date: 20190429